Low-energy planet escape orbit designing method based on invariant manifold and gravity assist

A technology of escape trajectory and design method, applied in space navigation equipment, transportation and packaging, etc., can solve problems such as inability to achieve fuel economy, invariant manifold branch selection and maneuvering pulse calculation

Inactive Publication Date: 2013-02-13
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0005] Aiming at the problems that the prior art cannot achieve the most fuel saving, invariant manifold branch selection and maneuvering pulse calculation, etc., the present invention proposes a low-energy planetary escape orbit design method based on invariant manifold and gravitational assistance

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  • Low-energy planet escape orbit designing method based on invariant manifold and gravity assist
  • Low-energy planet escape orbit designing method based on invariant manifold and gravity assist
  • Low-energy planet escape orbit designing method based on invariant manifold and gravity assist

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[0045] In order to better illustrate the purpose and advantages of the present invention, the content of the present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0046] Under the planar three-body model, the escape orbit of a low-energy planet based on the invariant manifold and gravitational assistance is as follows: figure 2 Shown: the probe first leaves the periodic orbit and approaches the departure star along the unstable manifold, and applies a pulse at a suitable position to leave the manifold, so as to achieve the required hyperbolic overspeed when escaping from the planetary influence sphere. Designing the optimal escape trajectory requires finding the manifold and the escape point with the minimum required pulse.

[0047] The low-energy planetary escape orbit design method using invariant manifold and gravity assistance is divided into three parts: periapsis calculation around the planet, periapsis requir...

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Abstract

The invention relates to low-energy planet escape orbit designing method based on an invariant manifold and a gravity assist, being particularly suitable for the design of a low-energy deep space exploration task orbit by using movable balance points and belonging to the field of an orbital maneuver technology of spacecrafts. The method is carried out by the following steps of: firstly obtaining an orbit state set of the invariant manifold at a periapsis place by introducing a periapsis poincare map based on sectional matching of the periapsis poincare map; and then calculating a maneuver pulse applied to each branch of the invariant manifold in the orbit state set by using a numeric iteration method according to an escape hyperbola excessive speed requirement needed for realizing interplanetary transit, and determining a branch of the invariant manifold corresponding to the escape with minimum fuel and the required maneuver pulse through the comparison of the maneuver pulses. The method disclosed by the invention has the advantages of simple calculation method, high calculation efficiency and the like and can provide reasonable and feasible initial value guess for a precise design.

Description

technical field [0001] The invention relates to a low-energy planetary escape trajectory design method based on invariant manifolds and gravitational assistance, which is particularly suitable for low-energy deep-space exploration mission trajectory design using dynamic balance points, and belongs to the technical field of spacecraft orbital maneuvering. Background technique [0002] The dynamic balance point and the nearby periodic orbit in the three-body dynamic system have important application value in space exploration missions because of their special position and dynamic characteristics. Up to now, many dynamic balance point orbit missions have been successfully implemented in the world, such as ISEE-3, SOHO, Genesis, etc. In recent years, some scholars have proposed the concept of using the dynamic balance point as a deep space exploration relay station, which provides a new transfer method for low-energy deep space exploration. The orbit design from the periodic or...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G99/00
Inventor 尚海滨崔平远吴伟仁王帅赵遵辉窦强
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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